摘要
对带弧形尾翼某导弹模型的实验研究表明 ,具有该种配置的导弹在以平衡攻角为中心俯仰振荡时 ,动稳定形态随来流马赫数 Ma∞ 变化 ,呈现非线性特点 ;亚音速时 ,稳定在平衡攻角状态 ;超音速时 ,存在临界马赫数 Macr,出现极限环运动。
The angular motion of a vehicle with wrap\|around fins around the static trim angle of attack is investigated using the wind tunnel free flight method. The angular motion varying with the change of Mach number presents non\|linear behavior: in the subsonic state, it is stable in the balance angle of attack; in the supersonic, there exists a critical Ma cr , and it becomes a circular limit motion. At the time, the flow pattern for pitching oscillation of the wrap\|around fin is revealed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2002年第4期321-323,共3页
Acta Aeronautica et Astronautica Sinica
